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公开(公告)号：US10030538B2
公开(公告)日：2018-07-24
申请号：US14933025
申请日：2015-11-05
Applicant: General Electric Company
Inventor： Wilhelm Ramon Hernandez , Daniel Edward Demers , Tyler Frederick Hooper , Victor Hugo Silva Correia , Troy Todd Dennis
Abstract: An apparatus and method of cooling a hot portion of a gas turbine engine, such as a rotor disk, by having a vane assembly with a cooling air passage and a flow control insert located within the cooling air passage defining a conduit. A turning nozzle is mounted to the vane and has a turning passage with an inlet and an outlet, the turning nozzle is fluidly coupled to the flow control insert outlet.
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公开(公告)号：US20170198602A1
公开(公告)日：2017-07-13
申请号：US14992432
申请日：2016-01-11
Applicant: General Electric Company
Inventor： Wilhelm Ramon Hernandez , Daniel Edward Demers , Tyler Frederick Hooper , Victor Hugo Silva Correia
CPC classification number: F01D25/12 , F01D5/189 , F01D9/041 , F01D11/005 , F05D2220/32 , F05D2240/11 , F05D2240/128 , F05D2240/81 , F05D2260/201 , Y02T50/671 , Y02T50/676
Abstract: An apparatus and method of cooling a hot portion of a gas turbine engine within a nozzle segment comprising an outer and inner band and at least one vane extending between the outer and inner band. The outer band includes a forward and aft cavity. The apparatus comprises a forward impingement baffle located within the forward cavity comprising a forward cooling chamber and an aft impingement baffle located within the aft cavity comprising an aft cooling chamber. Cooling air introduced into the forward cooling air chamber passes through impingement holes of the forward impingement baffle into a forward impingement chamber then passes through an aperture to the aft cooling air chamber, and then passes through the impingement holes of the aft impingement baffle into an aft impingement chamber.
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Patent Agency Ranking
公开(公告)号：US20170130604A1
公开(公告)日：2017-05-11
申请号：US14933025
申请日：2015-11-05
Applicant: General Electric Company
Inventor： Wilhelm Ramon Hernandez , Daniel Edward Demers , Tyler Frederick Hooper , Victor Hugo Silva Correia , Troy Todd Dennis
CPC classification number: F01D25/12 , F01D5/081 , F01D9/041 , F01D9/065 , F05D2220/32 , F05D2240/125 , F05D2240/128 , F05D2250/52 , F05D2250/71 , F05D2260/14 , F05D2260/201 , F05D2260/22141 , Y02T50/676
Abstract: An apparatus and method of cooling a hot portion of a gas turbine engine, such as a rotor disk, by having a vane assembly with a cooling air passage and a flow control insert located within the cooling air passage defining a conduit. A turning nozzle is mounted to the vane and has a turning passage with an inlet and an outlet, the turning nozzle is fluidly coupled to the flow control insert outlet.
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公开(公告)号：US09726024B2
公开(公告)日：2017-08-08
申请号：US14368962
申请日：2012-12-21
Applicant: GENERAL ELECTRIC COMPANY
CPC classification number: F01D5/188 , F01D5/189 , F01D9/02 , F05D2250/185 , F05D2260/201 , Y02T50/676
Abstract: An airfoil cooling circuit includes an impingement cooling circuit and a serpentine cooling circuit. An airfoil for use in a gas turbine engine having a cooling circuit which includes an impingement cooling circuit and a serpentine cooling circuit.
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公开(公告)号：US09506351B2
公开(公告)日：2016-11-29
申请号：US13852358
申请日：2013-03-28
Applicant: General Electric Company
Inventor： Joseph Steven Bubnick , Robert Joseph Bartz , Daniel Edward Demers , Robert Alan Frederick , Todd Stephen Heffron , Sean Michael Molleson
CPC classification number: F01D5/186 , F01D5/187 , F01D9/02 , F05D2240/303 , F05D2260/202 , Y02T50/673 , Y02T50/676
Abstract: A durable nozzle vane includes a leading edge where hot combustion gas impinges on the vane, a pressure side extending from the leading edge to a trailing edge and a suction side extending from the leading edge to the trailing edge, a blunt region along the suction side between the leading edge and a high curvature region, the blunt region having small curvature in the length between the leading edge and the high curvature region allowing for at least two rows of cooling apertures.
Abstract translation: 耐用的喷嘴叶片包括其中热燃烧气体撞击在叶片上的前缘，从前缘延伸到后缘的压力侧和从前缘延伸到后缘的吸力侧，沿着吸力侧的钝区 在前缘和高曲率区域之间，平坦区域在前缘和高曲率区域之间的长度上具有小曲率，允许至少两排冷却孔。
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公开(公告)号：US20140321977A1
公开(公告)日：2014-10-30
申请号：US13852358
申请日：2013-03-28
Applicant: General Electric Company
Inventor： Joseph Steven Bubnick , Robert Joseph Bartz , Daniel Edward Demers , Robert Alan Frederick , Todd Stephen Heffron , Sean Michael Molleson
CPC classification number: F01D5/186 , F01D5/187 , F01D9/02 , F05D2240/303 , F05D2260/202 , Y02T50/673 , Y02T50/676
Abstract: A durable nozzle vane includes a leading edge where hot combustion gas impinges on the vane, a pressure side extending from the leading edge to a trailing edge and a suction side extending from the leading edge to the trailing edge, a blunt region along the suction side between the leading edge and a high curvature region, the blunt region having small curvature in the length between the leading edge and the high curvature region allowing for at least two rows of cooling apertures.
Abstract translation: 耐用的喷嘴叶片包括其中热燃烧气体撞击在叶片上的前缘，从前缘延伸到后缘的压力侧和从前缘延伸到后缘的吸力侧，沿着吸力侧的钝区 在前缘和高曲率区域之间，平坦区域在前缘和高曲率区域之间的长度上具有小曲率，允许至少两排冷却孔。
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公开(公告)号：US20140348636A1
公开(公告)日：2014-11-27
申请号：US14368962
申请日：2012-12-21
Applicant: GENERAL ELECTRIC COMPANY
CPC classification number: F01D5/188 , F01D5/189 , F01D9/02 , F05D2250/185 , F05D2260/201 , Y02T50/676
Abstract: An airfoil cooling circuit includes an impingement cooling circuit and a serpentine cooling circuit. An airfoil for use in a gas turbine engine having a cooling circuit which includes an impingement cooling circuit and a serpentine cooling circuit
Abstract translation: 翼型冷却回路包括冲击冷却回路和蛇形冷却回路。 一种在具有冷却回路的燃气涡轮发动机中使用的翼型件，该冷却回路包括冲击冷却回路和蛇形冷却回路
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